Multi-parameter test platform and method for aero-engine stator adjustment mechanism

Abstract

The application provides an aero-engine stationary vane adjusting mechanism multi-parameter test test bed and a testing method thereof, comprising a workbench, a driving device, a testing device and a pneumatic force loading device; the testing device is provided with a rocker arm made of flexible metal material; a rocker arm shaft is connected with a pulley trolley and cooperates with a curved slide rail; the spatial motion track of the rocker arm shaft is completed by close cooperation of a first pulley trolley and a first curved slide rail, a second pulley trolley and a second curved slide rail; the spatial motion of a pin shaft of a rocker arm in a real compressor stationary vane adjusting mechanism is simulated, so that the rocker arm can be twisted and deformed, and the rocker arm shaft is connected with a blade shaft. The application integrates multiple test detection functions, solves the problems that the existing test equipment cannot simulate real motion pairs and transmission structures and cannot simulate complex working environments and the like, realizes multiple test research, reduces test cost and shortens test period.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing technology, and more particularly to a multi-parameter test bench and testing method for aero-engine stator adjustment mechanism. Background Technology

[0002] The stator blade adjustment mechanism is an important component of the aero-engine compressor. It is a multi-stage linkage mechanism located on the compressor casing. Its function is to adjust the angle of each stage of the compressor stator blades, thereby changing the intake direction and improving the engine surge problem.

[0003] The stator vane adjustment mechanism of an aero-engine has a complex structure. Due to the influence of initial machining and assembly precision, as well as friction and wear during operation, gaps are easily generated between the various moving pairs. In addition, the complex frictional resistance between the connecting rods at each stage can significantly affect the smoothness of the adjustment mechanism's movement and the stress it experiences, making it prone to malfunctions such as jamming. This has become a problem that urgently needs to be solved. Therefore, conducting experimental research on the aero-engine stator vane adjustment mechanism is of great significance for improving the performance of aero-engine compressors.

[0004] Existing test equipment for aero-engine stator adjustment mechanisms fails to simulate the actual kinematic pairs and connection structures, and fails to simulate the influence of multiple parameters such as aerodynamic loads and temperature under complex working environments, thus failing to meet test requirements.

[0005] For example, Chinese patent application number 202122306730.2 discloses a stator blade adjustment mechanism, a compressor, and a method for manufacturing a compressor test structure, but it differs significantly from existing stator blade adjustment mechanisms and cannot meet the requirements of existing technology tests. Similarly, Chinese patent application number 202210250995.1 discloses a dynamic characteristic simulation test bench for a single-stage stator blade adjustment mechanism, but this patent application does not consider the influence of the flexibility of key connecting parts, nor the influence of aerodynamic loads and temperature on the drag force. Finally, Chinese patent application number 202011269167.X discloses a stress-strain test bench for a stator blade adjustment mechanism considering temperature effects, but this patent application does not consider the influence of aerodynamic loads on the blade shaft and fails to simulate real kinematic pairs and connecting structures. For example, Chinese patent application No. 202011271048.8 discloses a test bench for friction and wear of the moving pair of the compressor stator blade adjustment mechanism, but the simplified model in the patent application cannot simulate the connection relationship of the real mechanism and does not take into account changes in working environment such as aerodynamic load and temperature. Summary of the Invention

[0006] The technical means employed in this invention are as follows:

[0007] A multi-parameter test bench for the stator blade adjustment mechanism of an aero-engine includes: a workbench, on which a test device is provided, the test device including an outer ring plate fixed on the workbench, and an inner ring plate and a slide rail support arranged parallel to the outer ring plate are respectively fixed on both sides of the outer ring plate;

[0008] The two ends of the blade shaft pass through the outer ring plate and the inner ring plate respectively, and an outer ring bushing and an inner ring bushing are respectively provided at the passage points;

[0009] Two first eddy current sensors and two second eddy current sensors are fixed on the sidewalls of the outer ring plate and the inner ring plate respectively. The two first eddy current sensors are arranged orthogonally, and their orthogonal intersection point is located on the axis of the blade shaft. The two second eddy current sensors are also arranged orthogonally, and their orthogonal intersection point is located on the axis of the blade shaft. The first eddy current sensors and the second eddy current sensors are used to measure the radial displacement of the blade shaft.

[0010] Ceramic heating elements are fixed to the sidewalls of the outer ring plate and the inner ring plate, which are respectively arranged opposite to each other.

[0011] The inner ring plate has a blade shaft angle sensor on the side away from the outer ring plate, which is connected to the end of the blade shaft. The blade shaft angle sensor is used to measure the rotation angle of the blade shaft.

[0012] The outer ring plate and the slide rail support are respectively fixed with a first curved slide rail and a second curved slide rail on their two side walls. The first curved slide rail and the second curved slide rail are respectively provided with a first pulley trolley and a second pulley trolley that slide with them. The first pulley trolley and the second pulley trolley are connected by a rocker arm shaft. The rocker arm shaft is connected to the blade shaft located below it by a rocker arm.

[0013] The workbench is also equipped with a drive device and a pneumatic loading device. The drive device is connected to the rocker arm shaft and is used to drive the rocker arm shaft and the first pulley carriage and the second pulley carriage at both ends of it to reciprocate within the first curved slide rail and the second curved slide rail. The pneumatic loading device is fixedly connected to the blade shaft and is used to apply radial force or axial force to the blade shaft.

[0014] Furthermore, the aerodynamic loading device includes an axial loading device and a radial loading device. Both the axial loading device and the radial loading device include: a fixed pulley bracket, a fixed pulley, a tension sensor, a weight, and a steel wire rope. The fixed pulley is fixedly mounted on the worktable via the fixed pulley bracket. One end of the horizontally positioned steel wire rope is fixedly connected to the blade shaft, and the other end extends vertically downward after being redirected by the fixed pulley. The weight is fixed to the tension sensor at the other end. The weight is used to apply tension to the blade shaft. The steel wire rope of the radial loading device is connected to the blade shaft via a radial force ring, and the extension direction of the horizontal portion of the steel wire rope is perpendicular to the axial direction of the blade shaft. The steel wire rope of the axial loading device is connected to the end of the blade shaft, and the extension direction of the horizontal portion of the steel wire rope coincides with the axial direction of the blade shaft.

[0015] Furthermore, the driving device includes a drive motor, which is fixedly mounted on the worktable via a motor bracket. The output end of the drive motor is connected to a motor connecting shaft via a first coupling. The motor connecting shaft passes through a first drive support fixed on the worktable and is connected to a crank-rocker mechanism, which is connected to the drive connecting shaft. The crank-rocker mechanism is used to convert the continuous rotation of the drive motor into the reciprocating rotation of the drive connecting shaft. The drive connecting shaft is connected to a main shaft, which is connected to the rocker arm shaft via a ball joint linkage mechanism. The ball joint linkage mechanism is used to drive the rocker arm shaft to reciprocate. The axial directions of the motor connecting shaft, the drive connecting shaft, and the main shaft are all parallel to the axial direction of the blade shaft.

[0016] Furthermore, one end of the spindle passes through the spindle bearing housing fixed on the worktable and is connected to the spindle angle encoder, which is used to measure the rotation angle of the spindle. The other end of the spindle is connected to the output end of the torque sensor through a third coupling, which is used to measure the torque of the spindle. The input end of the torque sensor is connected to the drive shaft through a second coupling.

[0017] Furthermore, the crank-connecting rod mechanism includes a crank, a connecting rod, and a rocker arm. One end of the crank is fixedly connected to the motor connecting shaft, the other end of the crank is hinged to one end of the connecting rod, the other end of the connecting rod is hinged to one end of the rocker arm, and the other end of the rocker arm is fixedly connected to the drive connecting shaft.

[0018] The ball joint mechanism includes a ball joint, one end of which is connected to the rocker arm shaft via a second joint bearing, and the other end of which is connected to a first joint bearing. The first joint bearing is connected to the main shaft crank fixed on the main shaft via a main shaft crank pin.

[0019] The present invention also discloses a test method for the resistance force of the stator adjustment mechanism of an aero-engine, the method comprising the following steps: S1: Start the test bench, control the drive motor to output at a constant speed, and after it works stably, collect the driving torque value of the torque sensor, which is the initial value of the resistance force.

[0020] S2: Change the clearance between the inner ring bushing and the outer ring bushing and the blade shaft, change the bushing material of the inner ring bushing and the outer ring bushing, change the thickness of the rocker arm, change the working temperature through the ceramic heating element, and change the axial and radial loads on the blade shaft through the aerodynamic loading device.

[0021] S3: Collect driving force and torque values ​​under different conditions;

[0022] S4: The change in the resistance force can be obtained by subtracting it from the initial value of the resistance force, and then the variation law of the resistance force under different parameters can be obtained.

[0023] The present invention also discloses a method for testing the joint clearance and contact stiffness of the stator adjustment mechanism of an aero-engine. The method includes the following steps: S1: Start the test bench and, after it is stable, collect the values ​​of the first eddy current sensor and the second eddy current sensor to obtain the axis trajectory of the blade shaft, and use strain gauges to measure the contact force of the blade shaft.

[0024] S2: Change the clearance between the inner ring bushing and the outer ring bushing and the blade shaft; change the working temperature through the ceramic heating element; change the axial and radial loads on the blade shaft through the aerodynamic loading device;

[0025] S3: Compare the changes in the blade axis trajectory and contact force with the contact stiffness under standard conditions to determine the correctness of the model and contact stiffness under different parameters.

[0026] The present invention also discloses a wear test method for the stator blade adjustment mechanism of an aero-engine, the method comprising the following steps: S1: cleaning the inner ring bushing and the outer ring bushing, and measuring the mass before the test using a balance;

[0027] S2: Start the test bench. After it has been working normally for a period of time, remove the inner ring bushing and the outer ring bushing and clean them. Then use the balance to measure the mass again.

[0028] S3: Calculate the mass difference between the two measurements, which is the wear amount of the inner ring bushing and the outer ring bushing.

[0029] The present invention also discloses a test method for the blade angle error of the stator adjustment mechanism of an aero-engine, the method comprising the following steps: S1: Start the test bench and, after it has stabilized, collect the values ​​of the main shaft angle encoder and the blade shaft angle encoder;

[0030] S2: Collect values ​​from multiple main shaft angle encoders and blade shaft angle encoders, obtain the relationship between the values ​​and time, and conduct kinematic modeling verification and error analysis research.

[0031] Compared with the prior art, the present invention has the following advantages:

[0032] 1. This invention integrates multiple testing and detection functions, solving the problem that existing testing equipment cannot simulate real kinematic pairs and transmission structures, as well as the influence of multiple parameters such as complex working environments. It realizes multiple experimental studies, reduces testing costs, and shortens the testing cycle.

[0033] 2. Compared with the existing test bench for the stator blade adjustment mechanism of aero-engines, the present invention simplifies the structural form of the stator blade adjustment mechanism, retains the key kinematic pairs and connection relationships, and takes into account working conditions such as aerodynamic loading and temperature, so as to reflect the actual motion of the stator blade adjustment mechanism. Attached Figure Description

[0034] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0035] Figure 1 This is a schematic diagram of the multi-parameter test bench for the stator blade adjustment mechanism of an aero-engine in this specific implementation.

[0036] Figure 2 This is a schematic diagram of the crank-connecting rod mechanism in this specific implementation.

[0037] Figure 3 This is a schematic diagram of the structure at the main shaft in this specific implementation.

[0038] Figure 4 This is a schematic diagram of the ball joint mechanism in this specific implementation.

[0039] Figure 5 This is an axial view of the testing device used in this specific implementation.

[0040] Figure 6 This is the main view of the test apparatus used in this specific implementation.

[0041] Figure 7 This is a cross-sectional view of the test apparatus used in this specific embodiment.

[0042] Figure 8 for Figure 7 Enlarged view of section A.

[0043] Figure 9 This is a schematic diagram of the curved slide rail and pulley trolley in this specific implementation.

[0044] In the diagram: Ⅰ. Testing device; Ⅱ. Drive device; Ⅲ. Pneumatic loading device; 1. Workbench; 2. Fixed pulley; 3. Drive motor; 4. Motor bracket; 5. First coupling; 6. Motor connecting shaft; 7. First drive bearing housing; 8. Crank; 9. Connecting rod; 10. Rocker arm; 11. Drive connecting shaft; 12. Second drive bearing housing; 13. Second coupling; 14. Torque sensor; 15. Torque sensor support; 16. Third coupling; 17. Main shaft; 18. Main shaft bearing housing; 19. Main shaft crank; 20. Main shaft crank pin; 21. First spherical bearing; 22. Main shaft angle encoder; 23. Ball joint connecting rod; 24. Second joint bearing; 25. Rocker arm shaft; 26. Rocker arm; 27. First pulley trolley; 28. First curved slide rail; 29. ​​Second pulley trolley; 30. Second curved slide rail; 31. Blade shaft; 32. Outer ring bushing; 33. Inner ring bushing; 34. Radial force pull ring; 35. Second eddy current bracket; 36. Second eddy current sensor; 37. First eddy current bracket; 38. First eddy current sensor; 39. Blade shaft angle encoder; 40. Inner ring plate; 41. Outer ring plate; 42. Slide rail support; 43. Ceramic heating element; 44. Fixed pulley bracket; 45. Tension sensor; 46. Weight; 47. Steel wire rope. Detailed Implementation

[0045] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0046] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0047] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of exemplary embodiments according to the invention. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0048] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0049] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention. The directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0050] For ease of description, spatial relative terms such as "above," "over," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation besides the orientation of the device as described in the figures. For example, if the device in the figures is inverted, a device described as "above" or "above" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0051] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0052] Example 1:

[0053] like Figures 1-9 As shown, a multi-parameter test bench for the stator blade adjustment mechanism of an aero-engine includes a workbench 1, on which a test device I, a drive device II, and an aerodynamic loading device III are installed; as shown Figures 5-7As shown, the testing device I includes an outer ring plate 41 fixed on the workbench 1, and an inner ring plate 40 and a slide rail support 42 arranged parallel to it are fixed on both sides of the outer ring plate 41 respectively; the two ends of the blade shaft 31 pass through the outer ring plate 41 and the inner ring plate 40 respectively, and an outer ring bushing 32 and an inner ring bushing 33 are respectively provided at the passage; two first eddy current sensors 38 and two second eddy current sensors 36 are fixed on the opposite side walls of the outer ring plate 41 and the inner ring plate 40 respectively by a first eddy current bracket 37 and a second eddy current bracket 37, and the two first eddy current sensors 38 are orthogonally arranged, and their orthogonal intersection point is located on the axis of the blade shaft 31, and the two second eddy current sensors 36 are orthogonally arranged, and their orthogonal intersection point is located on the axis of the blade shaft 31; the first eddy current sensors 38 and the second eddy current sensors 36 are used to measure the radial displacement of the blade shaft 31. Ceramic heating elements 43 are fixed on the opposite sidewalls of the outer ring plate 41 and the inner ring plate 40, respectively, and the ceramic heating elements 43 are used to heat the blade shaft 31. The inner ring plate 40 has a blade shaft angle sensor 39 connected to the end of the blade shaft 31 on the side away from the outer ring plate 41, and the blade shaft angle sensor 39 is used to measure the rotation angle of the blade shaft 31. A first curved slide rail 28 and a second curved slide rail 30 are fixed on the two sidewalls opposite to the slide rail support 42, respectively. A first pulley trolley 27 and a second pulley trolley 29 are respectively provided on the first curved slide rail 28 and the second curved slide rail 30, and the first pulley trolley 27 and the second pulley trolley 29 are connected by a rocker arm shaft 25. The rocker arm shaft 25 is connected to the blade shaft 31 located below it by a rocker arm 26, and the rocker arm 26 is made of flexible metal material.

[0054] like Figure 9 As shown, the first curved slide rail 28 and the second curved slide rail 30 are generally arc-shaped. The first slide rail 28 and the second slide rail 30 form a complementary structure. The axis of the wheel of the first pulley trolley 27 is perpendicular to the bottom of the first curved slide rail 28, and the axis of the wheel of the second pulley trolley 29 is perpendicular to the bottom of the second curved slide rail 30. The spatial movement trajectory of the rocker arm shaft 25 is completed by the close cooperation of the first pulley trolley 27 with the first curved slide rail 28, the second pulley trolley 29 and the second curved slide rail 30, simulating the spatial movement of the rocker arm pin in the real compressor stator vane adjustment mechanism, so that the rocker arm 26 can undergo torsional deformation.

[0055] The drive device II is connected to the rocker arm shaft 25 and is used to drive the rocker arm shaft 25 and the first pulley trolley 27 and the second pulley trolley 29 at both ends to reciprocate within the first curved slide rail 28 and the second curved slide rail 30. The aerodynamic loading device III is fixedly connected to the blade shaft 31 and is used to apply radial force or axial force to the blade shaft 31.

[0056] like Figure 1 As shown, the aerodynamic loading device III includes an axial loading device and a radial loading device. Both the axial loading device and the radial loading device include: a fixed pulley bracket 44, a fixed pulley 2, a tension sensor 45, a weight 46, and a steel wire rope 47. The fixed pulley 2 is fixedly mounted on the workbench 1 via the fixed pulley bracket 44. One end of the horizontally arranged steel wire rope 47 is fixedly connected to the blade shaft 31, and the other end extends vertically downward after being redirected by the fixed pulley 2, and a weight 46 is fixed to it via the tension sensor 45. The weight 46 is used to apply tension to the blade shaft 31. The steel wire rope 47 of the radial loading device is connected to the blade shaft 31 via a radial force ring 34, and the extension direction of the horizontal portion of the steel wire rope 47 is perpendicular to the axial direction of the blade shaft 31. The steel wire rope 47 of the axial loading device is connected to the end of the blade shaft 31, and the extension direction of the horizontal portion of this steel wire rope 47 coincides with the axial direction of the blade shaft 31.

[0057] like Figures 2-4As shown, the drive device II includes a drive motor 3, which is fixedly mounted on the workbench 1 via a motor bracket 4. The output end of the drive motor 3 is connected to a motor connecting shaft 6 via a first coupling 5. The motor connecting shaft 6 passes through a first drive support 7 fixed on the workbench 1 and is connected to a crank-rocker mechanism. The crank-rocker mechanism is connected to the drive connecting shaft 11. The crank-rocker mechanism is used to convert the continuous rotation of the drive motor 3 into the reciprocating rotation of the drive connecting shaft 11. The crank-connecting rod mechanism includes a crank 8, a connecting rod 9, and a rocker arm 10. One end of the crank 8 is fixedly connected to the motor connecting shaft 6, and the other end of the crank 8 is hinged to the connecting rod 9. One end of the connecting rod 9 is hinged to the rocker arm 10, and one end of the rocker arm 10 is fixedly connected to the drive connecting shaft 11. The crank 8, rocker arm 10, and connecting rod 9 are of mutually compatible lengths. The stroke ratio coefficient k of the crank-rocker mechanism is 1, and the average reciprocating oscillation speed of the rocker arm 10 is the same. The drive connecting shaft 11 passes through the second drive support seat 12 and is connected to the main shaft 17. The second drive support seat 12 is fixedly mounted on the worktable 1 and is used to support the drive connecting shaft 11. The main shaft 17 is connected to the rocker arm shaft 25 through a ball joint connecting rod mechanism. The ball joint connecting rod mechanism is used to drive the rocker arm shaft 25 to reciprocate. The ball joint connecting rod mechanism includes a ball joint connecting rod 23. One end of the ball joint connecting rod 23 is connected to the rocker arm shaft 25 through a second joint bearing 24, and the other end of the ball joint connecting rod 23 is connected to a first joint bearing 21. The first joint bearing 21 is connected through... The main shaft crank pin 20 is connected to the main shaft crank 19. The axial directions of the motor connecting shaft 6, the drive connecting shaft 11, and the main shaft 17 are all parallel to the axial direction of the blade shaft 31. One end of the main shaft 17 passes through the main shaft bearing seat 18 fixed on the worktable 1 and is connected to the main shaft angle encoder 22. The main shaft angle encoder 22 is used to measure the rotation angle of the main shaft 17. The other end of the main shaft 17 is connected to the output end of the torque sensor 14 through the third coupling 16. The torque sensor 14 is fixed on the worktable 1 through the torque sensor support 15. The torque sensor 14 is used to measure the torque of the main shaft 17. The input end of the torque sensor 14 is connected to the drive connecting shaft 11 through the second coupling 13.

[0058] This application simulates a stage of the compressor stator vane adjustment mechanism in a real aero-engine, simplifying its structure and stress conditions while retaining key kinematic pairs. The RSSCR transmission chain is designed as follows: the main shaft crank 19 rotates with the main shaft 17, forming a rotary joint R; the ball joint connecting rod 23 has a first joint bearing 21 and a second joint bearing 24 at both ends, forming two ball joints SS; one end of the rocker arm 26 can rotate around the rocker arm shaft 25 and move radially along it, forming a cylindrical joint C; the other end of the rocker arm 26 drives the blade shaft 31 to rotate axially, forming a rotary joint R.

[0059] The working principle of this invention is as follows: Power is provided by the drive motor 3, which drives the crank-rocker mechanism to move. The crank-rocker mechanism converts the continuous rotation of the drive motor 3 into the reciprocating swing of the drive connecting shaft 11, thereby driving the main shaft 17 to drive the ball joint connecting rod 23 to swing back and forth. The ball joint connecting rod 23 drives the rocker arm shaft 25, rocker arm 26, and blade shaft 31 to swing back and forth. The spatial movement of the rocker arm pin in the real compressor stationary blade adjustment mechanism is simulated by the movement of the first sliding carriage 27 and the second sliding carriage 29 along a certain trajectory in the first curved slide rail 28 and the second curved slide rail 30, respectively. The spatial movement trajectory of the rocker arm shaft 25 is ensured by the close cooperation of the first pulley carriage 27, the first curved slide rail 28, the second pulley carriage 29, and the second curved slide rail 30, so that the rocker arm 26 can undergo torsional deformation, thereby changing the movement trajectory of the blade shaft 31. During this process, the resistance force, friction wear, and angular offset of the blade shaft 31 are measured.

[0060] Example 2:

[0061] like Figures 1-9 As shown, a test method for the resistance force of an aero-engine stator blade adjustment mechanism is based on the test bench disclosed in Example 1. The method includes the following steps: starting the test bench, controlling the drive motor 3 to output at a constant speed, and after it stabilizes, collecting the driving torque value of the torque sensor 14, which is the initial value of the resistance force.

[0062] S2: Change the clearance between the inner ring bushing 33 and the outer ring bushing 32 and the blade shaft 31, change the bushing material of the inner ring bushing 33 and the outer ring bushing 32, change the thickness of the rocker arm 26, change the working temperature through the ceramic heating plate 43, and change the axial and radial loads of the blade shaft 31 through the aerodynamic loading device III.

[0063] S3: Collect driving force and torque values ​​under different conditions;

[0064] S4: The change in the resistance force can be obtained by subtracting it from the initial value of the resistance force, and then the variation law of the resistance force under different parameters can be obtained.

[0065] Example 3:

[0066] like Figures 1-9 As shown, a test method for joint clearance and contact stiffness of aero-engine stator adjustment mechanism is based on the test bench disclosed in Example 1. The method has the following steps: S1: Start the test bench and after it is stable, collect the values ​​of the first eddy current sensor 38 and the second eddy current sensor 36 to obtain the axis trajectory of the blade shaft 31, and use strain gauges to measure the contact force of the blade shaft 31.

[0067] S2: Change the clearance between the inner ring bushing 33 and the outer ring bushing 32 and the blade shaft 31; change the working temperature through the ceramic heating plate 43; and change the axial and radial loads on the blade shaft 31 through the aerodynamic loading device III.

[0068] S3: Compare the changes in the trajectory of the blade shaft 31 center and the contact force, and compare them with the contact stiffness under standard conditions to obtain the correctness of the model and contact stiffness under different parameters.

[0069] Example 4:

[0070] like Figures 1-9 As shown, a wear test method for an aero-engine stator blade adjustment mechanism is based on the test bench disclosed in Example 1. The method includes the following steps: S1: Clean the inner ring bushing 33 and the outer ring bushing 32, and use a balance to measure the mass before the test;

[0071] S2: Start the test bench and after it has been working normally for a period of time, remove the inner ring bushing 33 and the outer ring bushing 32 and clean them. Then use the balance to measure the mass again.

[0072] S3: The difference in mass between the two measurements is the wear amount of the inner ring bushing 33 and the outer ring bushing 32.

[0073] Example 5:

[0074] like Figures 1-9 As shown, a test method for the blade angle error of the stator adjustment mechanism of an aero-engine is based on the test bench disclosed in Example 1. The method has the following steps: S1: Start the test bench and after it is stable, collect the values ​​of the main shaft angle encoder 22 and the blade shaft angle encoder 39.

[0075] S2: Collect values ​​from multiple main shaft angle encoders and blade shaft angle encoders, obtain the relationship between the values ​​and time, and conduct kinematic modeling verification and error analysis research.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A multi-parameter test bench for the stator blade adjustment mechanism of an aero-engine, characterized in that, The device includes a workbench, on which a testing device is provided. The testing device includes an outer ring plate fixed on the workbench, and an inner ring plate and a slide rail support arranged parallel to the outer ring plate are respectively fixed on both sides of the outer ring plate. The two ends of the blade shaft pass through the outer ring plate and the inner ring plate respectively, and an outer ring bushing and an inner ring bushing are respectively provided at the passage points; Two first eddy current sensors and two second eddy current sensors are respectively fixed on the sidewalls of the outer ring plate and the inner ring plate, which are arranged opposite to each other. The two first eddy current sensors are arranged orthogonally, and their orthogonal intersection point is located on the axis of the blade shaft. The two second eddy current sensors are also arranged orthogonally, and their orthogonal intersection point is located on the axis of the blade shaft. The first eddy current sensors and the second eddy current sensors are used to measure the radial displacement of the blade shaft. Ceramic heating elements are fixed to the sidewalls of the outer ring plate and the inner ring plate, which are respectively arranged opposite to each other. The inner ring plate has a blade shaft angle sensor on the side away from the outer ring plate that is connected to the end of the blade shaft. The blade shaft angle sensor is used to measure the rotation angle of the blade shaft. The outer ring plate and the slide rail support are respectively fixed with a first curved slide rail and a second curved slide rail on their two side walls. The first curved slide rail and the second curved slide rail are respectively provided with a first pulley trolley and a second pulley trolley that slide with them. The first pulley trolley and the second pulley trolley are connected by a rocker arm shaft. The rocker arm shaft is connected to the blade shaft located below it by a rocker arm. The workbench is also equipped with a drive device and a pneumatic loading device. The drive device is connected to the rocker arm shaft and is used to drive the rocker arm shaft and the first pulley carriage and the second pulley carriage at both ends of it to reciprocate within the first curved slide rail and the second curved slide rail. The pneumatic loading device is fixedly connected to the blade shaft and is used to apply radial force or axial force to the blade shaft.

2. The multi-parameter test bench for the aero-engine stator blade adjustment mechanism according to claim 1, characterized in that, The aerodynamic loading device includes an axial loading device and a radial loading device. Both the axial loading device and the radial loading device include: a fixed pulley bracket, a fixed pulley, a tension sensor, a weight, and a steel wire rope. The fixed pulley is fixedly mounted on the worktable via the fixed pulley bracket. One end of the horizontally positioned steel wire rope is fixedly connected to the blade shaft, and the other end extends vertically downward after being redirected by the fixed pulley. The weight is fixed to the tension sensor at the other end. The weight is used to apply tension to the blade shaft. The steel wire rope of the radial loading device is connected to the blade shaft via a radial force ring, and the extension direction of the horizontal portion of the steel wire rope is perpendicular to the axial direction of the blade shaft. The steel wire rope of the axial loading device is connected to the end of the blade shaft, and the extension direction of the horizontal portion of the steel wire rope coincides with the axial direction of the blade shaft.

3. The multi-parameter test bench for the aero-engine stator blade adjustment mechanism according to claim 1, characterized in that, The driving device includes a drive motor, which is fixedly mounted on the worktable by a motor bracket. The output end of the drive motor is connected to a motor connecting shaft via a first coupling. The motor connecting shaft passes through a first drive support fixed on the worktable and is connected to a crank-rocker mechanism, which is connected to the drive connecting shaft. The crank-rocker mechanism is used to convert the continuous rotation of the drive motor into the reciprocating rotation of the drive connecting shaft. The drive connecting shaft is connected to a main shaft, which is connected to the rocker arm shaft via a ball joint connecting rod mechanism. The axial directions of the motor connecting shaft, the drive connecting shaft, and the main shaft are all parallel to the axial direction of the blade shaft.

4. The multi-parameter test bench for the aero-engine stator blade adjustment mechanism according to claim 3, characterized in that, One end of the spindle passes through the spindle bearing housing fixed on the worktable and is connected to the spindle angle encoder, which is used to measure the rotation angle of the spindle. The other end of the spindle is connected to the output end of the torque sensor through a third coupling, which is used to measure the torque of the spindle. The input end of the torque sensor is connected to the drive shaft through a second coupling.

5. The multi-parameter test bench for the aero-engine stator blade adjustment mechanism according to claim 3, characterized in that, The crank-connecting rod mechanism includes a crank, a connecting rod, and a rocker arm. One end of the crank is fixedly connected to the motor connecting shaft, the other end of the crank is hinged to one end of the connecting rod, the other end of the connecting rod is hinged to one end of the rocker arm, and the other end of the rocker arm is fixedly connected to the drive connecting shaft. The ball joint mechanism includes a ball joint, one end of which is connected to the rocker arm shaft via a second joint bearing, and the other end of which is connected to a first joint bearing. The first joint bearing is connected to the main shaft crank fixed on the main shaft via a main shaft crank pin.

6. A test method for measuring the drag force of an aero-engine stator blade adjusting mechanism, characterized in that, Based on the multi-parameter test bench for the aero-engine stator blade adjustment mechanism as described in claim 4, the method comprises the following steps: S1: Start the test bench and control the drive motor to output at a constant speed. After it stabilizes, the driving torque value of the torque sensor is collected as the initial value of the resistance force. S2: Change the clearance between the inner ring bushing and the outer ring bushing and the blade shaft, change the bushing material of the inner ring bushing and the outer ring bushing, change the thickness of the rocker arm, change the working temperature through the ceramic heating element, and change the axial and radial loads on the blade shaft through the aerodynamic loading device. S3: Collect driving force and torque values ​​under different conditions; S4: The change in the resistance force can be obtained by subtracting it from the initial value of the resistance force, and then the variation law of the resistance force under different parameters can be obtained.

7. A method for testing the joint clearance and contact stiffness of an aero-engine stator blade adjusting mechanism, characterized in that, Based on the multi-parameter test bench for the aero-engine stator vane adjustment mechanism as described in any one of claims 1-5, the method comprises the following steps: S1: Start the test bench and wait for it to stabilize. Collect the values ​​of the first eddy current sensor and the second eddy current sensor to obtain the blade shaft center trajectory. Use strain gauges to measure the contact force of the blade shaft. S2: Change the clearance between the inner ring bushing and the outer ring bushing and the blade shaft; change the working temperature through the ceramic heating element; change the axial and radial loads on the blade shaft through the aerodynamic loading device; S3: Compare the changes in the blade axis trajectory and contact force with the contact stiffness under standard conditions to determine the correctness of the model and contact stiffness under different parameters.

8. A test method for wear of the stator vane adjustment mechanism of an aero-engine, characterized in that, Based on the multi-parameter test bench for the aero-engine stator blade adjustment mechanism as described in any one of claims 1 to 5, the method comprises the following steps: S1: Clean the inner ring bushing and the outer ring bushing, and measure their mass before the test using a balance; S2: Start the test bench. After it has been working normally for a period of time, remove the inner ring bushing and the outer ring bushing and clean them. Then use the balance to measure the mass again. S3: Calculate the mass difference between the two measurements, which is the wear amount of the inner ring bushing and the outer ring bushing.

9. A test method for blade angle error of aero-engine stator adjustment mechanism, characterized in that, Based on the multi-parameter test bench for the aero-engine stator blade adjustment mechanism as described in claim 4, the method comprises the following steps: S1: Start the test bench and, after it has stabilized, collect the values ​​of the main shaft angle encoder and the blade shaft angle encoder. S2: Collect values ​​from multiple main shaft angle encoders and blade shaft angle encoders, obtain the relationship between the values ​​and time, and conduct kinematic modeling verification and error analysis research.

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